Satellite positioning system receivers and methods

ABSTRACT

A satellite positioning system receiver having a battery, wherein the receiver is programmed to determine ( 310 ) whether the receiver is connected to a power supply other than its battery, to begin continuous reception ( 320 ) of satellite positioning system navigation data when the receiver is connected to a power supply other than its battery, and to store ( 330 ) the navigation data received in memory of the receiver.

CROSS REFERENCE TO REALTED APPLICATIONS

The present application is a division of commonly assigned U.S.application Ser. No. 10/606,555 filed on 26 Jun. 2003 now abandoned,from which benefits under 35 USC 120 are hereby claimed and the contentsof which are incorporated herein by reference.

FIELD OF THE DISCLOSURE

The present disclosure relates generally to satellite positioning system(SPS) receivers, and more particularly to acquiring satelliteinformation used for approximating the initial position of and locatingSPS receivers, for example, Global Positioning System (GPS) enabledmobile wireless communications subscriber devices, and methods.

BACKGROUND

The Global Positioning System (GPS) is a satellite based location andtime transfer system developed by the United States government andavailable free of charge to all users. Other satellite positioningsystems (SPS) have also been or are being developed, including theGlonass satellite system in Russia and the Galileo system in Europe.

The location of an SPS receiver is based upon a one-way ranging betweenthe SPS receiver and several satellites, which transmit signals havingthe times-of-transmission and orbital parameters for their respectivetime variable locations-in-space. An SPS receiver acquires satellitesignals by correlating internal replica signals to carrier frequenciesand distinguishable codes for each of several in-view satellites. Whensatellite signals have been acquired, the SPS receiver uses time and theorbital parameter information from the acquired satellites for measuringranges to the satellites, preferably four or more satellites. Thesemeasured ranges are called pseudoranges because they include a termcaused by a time error of the SPS receiver clock.

The SPS satellite pseudoranges are measured by determining phase offsetsbetween pseudorandom (PRN) codes of the received satellite signals andthe internal replica PRN codes referenced to the SPS receiver clock.Some SPS receivers measure and integrate the carrier phases of thesatellite signals in order to reduce noise on the measured phaseoffsets. The SPS receiver then determines an SPS-based time bymonitoring the SPS signals until a TOW field is decoded. The SPS-basedtime is used to determine the times that the phase offsets weremeasured. The measurement times are then used with ephemeris datareceived from the satellites for calculating instantaneouslocations-in-space of several satellites and for linearizing locationequations relating the calculated locations-in-space to the measuredpseudoranges. Having four or more linearized location equations for fouror more satellites, respectively, SPS receivers can resolve their3-dimensional geographical location and correct the time error in theirinternal clocks.

It is known generally to use almanac and ephemeris information stored onSPS receivers to speed the acquisition of satellites. The almanac datacontains coefficients to Kepler's equations of satellite motion and isuseful for computing which satellites are visible at a particular time.The almanac data may also be used for computing satellite location andvelocity vectors, from which satellite Doppler estimates may be computedfor aiding signal acquisition. The almanac data provides low-resolutionsatellite position accuracy, which is typically no better than about 1kilometer when fresh. Almanac data however contains a relatively smallnumber of bytes, approximately 1200 bytes for 32 satellites, and almanacdata is useful for 6 months to 1 year depending on whether satellitesare re-positioned or new satellites have been added or removed from theconstellation. In the GPS constellation, each satellite broadcastsalmanac data, which is updated every few days, for all GPS satellites ona twelve and one-half minute cycle.

Ephemeris data is similar to almanac data but provides far more accuratesatellite position information, which is accurate to within severalmeters if the ephemeris data is not more than a few hours old. Theaccuracy of satellite position information derived from ephemeris datadegrades with time. SPS receivers typically use ephemeris data forcomputing precise satellite locations, which may be used for positioncomputation when combined with SPS receiver measured pseudorangeinformation. A GPS constellation ephemeris data set for one satellite isapproximately 72 bytes of data, and thus ephemeris data for all 32 GPSsatellites requires about 2304 bytes of data storage space. In the GPSconstellation, each satellite broadcasts its own ephemeris data everythirty-seconds. An SPS receiver must acquire a satellite in order toobtain its ephemeris data.

In a typical GPS receiver, for example, in GPS enabled cellularcommunications and stand-alone navigation devices, the time to acquirenew almanac data directly from a satellite requires more than twelve anda half minutes (12.5 minutes). Operating GPS receivers for therelatively long period required to obtain almanac data directly from asatellite draws substantially charge from the battery, which isundesirable in many applications including GPS enabled cellulartelephones. The time required to obtain ephemeris data in this manner iscomparatively small, at approximately thirty seconds (30 sec.).

It is known to provide almanac information to GPS enabled radiocommunications devices in an over-the-air radio message, as disclosed,for example, in U.S. Pat. No. 6,064,336 entitled “GPS Receiver UtilizingA Communication Link”, among other patents and publications. In someinstances, however, it is undesirable to use almanac information or toobtain it in an over-the-air message.

It is also known to provide ephemeris information to GPS enabled radiocommunications devices in an over-the-air radio message, as performed,for example, by the Motorola Eagle GPS receivers. In prior art FIG. 1,GPS satellite ephemeris and almanac information 10 is transmitted from acellular communications network base-station 12 to a wireless subscriberdevice 14 using an over-the-air communications protocol. Wirelesssubscriber device 14 contains a GPS receiver 16 with an antenna, acellular transceiver 20, and two databases, stored in memory, to storeephemeris data 22 and almanac data 24. The GPS receiver 16 can acquireboth almanac and ephemeris data directly from GPS satellites via antenna18 and store them into the almanac database 24 and ephemeris database22. In addition, the cellular transceiver 20 can acquire fresh almanacand ephemeris data 10 from the cellular network via over-the-airmessages.

Transmitting satellite almanac and ephemeris data over a communicationslink however requires costly network infrastructure. Additionally,relatively long data strings are required for the transmission ofephemeris and almanac data, and the management of requesting and storingthe data derived from over-the-air messages is cumbersome. Other GPSreceiver applications, including vehicle navigation, do not include aradio, which could be used for receiving over-the-air assistancemessages. For these and other reasons, in at least some applications, itis undesirable to obtain almanac data from over-the-air assistancemessages.

U.S. Pat. No. 6,437,735 entitled “Position Detection System Integratedinto Mobile Terminal” discloses receiving ephemeris data at a mobile GPSreceiver either directly from GPS satellites or from a wirelesscommunications network, and transforms the ephemeris data to almanacinformation by scaling and masking ephemeris parameters to formcorresponding almanac parameters, which are stored on the GPS receiverfor positioning determination. Almanac data derived in this manner isbelieved have substantial errors, for example, accumulated error in thealong-track direction, which will likely produce unacceptable resultsover very long time periods.

The various aspects, features and advantages of the disclosure willbecome more fully apparent to those having ordinary skill in the artupon careful consideration of the following Detailed Description thereofwith the accompanying drawings described below.

BRIEF DESCRIPTION OF THE DRAWINGS

FIG. 1 is prior art system architecture for communicating GPS satellitealmanac and ephemeris information from networks to subscriber devices.

FIG. 2 is a schematic block diagram of an exemplary GPS receiver.

FIG. 3 is a process flow diagram.

FIG. 4 is another schematic block diagram of an exemplary GPS receiver.

FIG. 5 is an exemplary signal having information frames.

FIG. 6 is schematic illustration of a process for deriving satelliteorbital information from ephemeris information.

FIG. 7 is a schematic illustration of a process for updating almanacinformation with ephemeris information.

FIG. 8 is a plot of satellite position vector differences betweenalmanac-derived satellite positions and ephemeris-derived satellitepositions, as a function of almanac and ephemeris age.

FIG. 9 is a plot of satellite velocity vector differences betweenalmanac-derived satellite velocities and ephemeris-derived satellitevelocities, as a function of almanac and ephemeris age.

FIG. 10 is a plot of satellite position vector differences betweenalmanac-derived satellite positions and ephemeris-derived satellitepositions, for the case of fresh ephemeris and an almanac that is 40days old, as a function of ephemeris age in days.

FIG. 11 is a plot of satellite velocity vector differences betweenalmanac-derived satellite velocities and ephemeris-derived satellitevelocities, for the case of fresh ephemeris and an almanac that is 40days old, as a function of ephemeris age in days.

DETAILED DESCRIPTION

According to one aspect of the disclosure, a satellite positioningsystem (SPS) receiver automatically acquires or attempts to acquirealmanac data any time the SPS receiver is connected to external power,for example, to a battery charger or a car-kit adaptor. In this mode ofoperation, the SPS receiver continuously operates the GPS receiver todemodulate almanac data or other information, for example, from signalsreceived directly from a satellite or from some other source, whileconnected to the external power supply.

In FIG. 2, a GPS receiver 210 in a cellular handset 220 acquiressatellite navigation data directly from a GPS satellite 230 via GPSantenna 232. Once received, the satellite navigation data, for example,almanac and/or ephemeris data, is stored in memory, for example, inephemeris database 234 and almanac database 236. The GPS receiver 210 iscontinuously powered ON and attempting to demodulate ephemeris andalmanac data directly from GPS satellites 230 as long as power isapplied to the handset externally via an external charger connector 240.The external power may be from a battery charger, a cigarette lighteradapter, a hands-free car adaptor, or similar external power supply thatsupplies power to the entire phone instead of from the batteriesinternal to the SPS receiver.

In the process diagram 300 of FIG. 3, at block 310, a determination ismade whether the SPS receiver, for example, embedded in a cellularsubscriber device, is connected to a power supply other than itsinternal battery. At block 320, satellite navigation information isreceived if the receiver is coupled to the external power supply. Thesatellite information, for example, ephemeris and/or almanac data, maybe received directly from a satellite or alternatively from some othersource without regard to battery power consumption since the receiverdoes not operate on battery power. At block 330, the satellitenavigation information is stored on the receiver, for example, inmemory.

In one embodiment, reception of satellite positioning system navigationdata begins when the receiver is connected to a power supply other thanits battery. Generally, the reception of satellite positioning systemnavigation data is discontinued if the receiver is reconnected to itsbattery. In some embodiments, however, it may be desirable to continuereception of the SPS navigation data upon reconnecting the SPS receiverto its battery until reception of the navigation data is complete. Insome embodiment, navigation data, for example almanac data, isdownloaded directly from the satellite only if the receiver is coupledto external power.

In FIG. 3, at block 340, a determination is made whether battery powerhas been re-connected, for example, upon disconnecting the externalpower source. If the download of satellite data is incomplete at block350, a determination is made at block 360 whether a condition issatisfied that would require or justify completion of the download underbattery power. The condition assessed at block 360 may be that thedownloading data is essential or that the download is nearly complete,which may be determined, for example, by assessing whether apredetermined portion, or percentage, of the navigation data has alreadybeen received. In FIG. 3, at block 370, the download is ended if thecondition is not satisfied, and at block 380 the download is completedif the condition is satisfied.

According to another aspect of the disclosure, an SPS receiver isoperated synchronously with an expected time of arrival of information,for example, satellite almanac and/or ephemeris information. Thusoperated, the SPS receiver does not remain idle and consume power whennot receiving information. FIG. 4 illustrates a schematic block diagramof an exemplary SPS receiver having a real-time clock that controlsoperation of the GPS receiver synchronously with expected arrival timesof information.

FIG. 5 is an exemplary multi-frame signal, for example, a GPS navigationmessage, although the message could be any other signal. GPS signals aretransmitted on predictable schedules, and thus upon acquiring a GPSsignal, the GPS receiver may synchronize its operation to receive onlyinformation of interest in the signal. In FIG. 5, for example, thereceive function of the GPS receiver is powered OFF during the arrivalof frames SF1-SF3, and the receive function of the GPS receiver is powerON during the arrival of frames SF4 and SF5 to permit reception anddemodulation of the desired data almanac. The almanac data is known tooccupy only sub frames 4 and 5, and not occupy subframes 1 through 3.The almanac data is commutated over 25 sequential sets of subframes 4and 5 in order to broadcast the almanac data. The data structure shownin FIG. 5 begins synchronously with every 30-second epoch from the startof the week. Thus, the time of the 1^(st) bit of subframe 1 is alwaystransmitted some integer number times 30 seconds since the beginning ofthe week (n*30 sec). Likewise, the 1^(st) bit of subframe 2 is known tobegin 6 seconds later, or at time T=n*30+6 seconds, since the start ofthe week. Subframe 3 begins at T=n*30+12 seconds, subframe 4 begins atT=n*30+18 seconds, and subframe 5 begins at T=n*30+24 seconds since thebeginning of the week. Consequently, if the GPS receiver real-time clockis previously synchronized with relatively accurate time, it can beprogrammed to power on at the beginning of subframe 4 and power-off atthe end of subframe 5, demodulating only bits for those subframes, andacquiring fresh almanac data while minimizing its power consumption. 25sets of subframes 4 and 5 are required to obtain a complete issue ofalmanac data. In one embodiment, the GPS receiver receives navigationinformation while tracking a satellite.

In one embodiment, the GPS receiver is operated synchronously with anexpected arrival of ephemeris and/or almanac information in a GPSnavigation message transmitted by a GPS satellite or other source, likea repeater. In other embodiments, the GPS receiver operatessynchronously with an expected time of arrival of clock correctioninformation, ionospheric correction information, tropospheric correctioninformation, universal time coordinate offset correction information, orother having a scheduled time of arrival.

Generally, the GPS receiver may perform other operations during timeperiods when the receive function disabled, for example, during thearrival of frames SF1-SF3 in FIG. 5. More particularly, during periodswhen the GPS receiver is not receiving, the GPS receiver may operate toprocess signals received previously.

Navstar document ICD-GPS-200, Revision C, updated Oct. 11, 1999, whichis hereby incorporated by reference in its entirety, list on pp. 87 and96 the ephemeris parameters and on page 108 the almanac parameters.

Satellite almanac data is useful in computing acquisition assistanceinformation, such as satellite Doppler and code phase estimates andsatellite visibility estimates as a function of time. The almanac datais tailored or optimized for a particular epoch time. The epoch time isidentified by a parameter TOA (time of almanac), which is the epoch timedescribed as the number of seconds into the week, and an almanac weeknumber WNA. The GPS time clock and week numbers began at week numberzero and time zero on Jan. 5, 1980, week numbers increment one counteach week, rolling over after 1024 weeks, while the GPS time clockincrements one second each second, clearing at the start of the nextweek. 604800 seconds are accumulated each week. An almanac week numberWNA and TOA identify precisely the reference time for the almanac withan ambiguity of the 256-week period of the almanac week number. Thealmanac week number is 8 bits of the 10 bit GPS week number producing a256 week repeat time. The almanac equations for determining satelliteposition vs. time are driven by a time difference, that being the timein seconds between the current time and the TOA, accounting for weeknumber differences as well. A notation for how this is accomplished withalmanac is shown in Eqn. (1), in which a function translates the almanacinto a 3 dimensional satellite XYZ position vector in theearth-centered-earth-fixed (ECEF) coordinate frame as a function of time“t”, week number “wk”, for a particular satellite “sv”, and where thefunction SVPOS_alm uses the almanac satellite position equationsdescribed earlier.SVPosXYZ _(—) alm[sv]=SVPOS _(—) alm(t,wk,sv)  (1)The 3-dimensional vector SatPosXYZ_alm can be written asSVPosXYZ_alm=[SVPosX, SVPosY, SVPosZ], where the SVPosX component is theX-axis element, SVPosY is the Y-axis element, and SVPosZ is the Z-axiselement. The almanac equations translate time and week number intosatellite velocity vector as shown below in Eqn. (2).SVVelXYZ _(—) alm[sv]=SVVEL _(—) alm(t,wk,sv)  (2)The returned velocity vector is a 3-dimensional vector in the ECEFCartesian coordinate system indicating the satellite velocity at theinstantaneous time epoch “t”.

The satellite ephemeris data is also targeted and optimized for aparticular epoch time, called time of ephemeris, or TOE. The ephemerisdata is useful for computing precise satellite position data accurate towithin a few meters, provided the time difference between the currenttime “t” and TOE is within +/−2 hours under normal conditions. When thedifference between time t and TOE is within the range −7200seconds<=t−TOE<=+7200 seconds, the ephemeris data reliably computes thesatellite position vector and velocity vector data to a precisionnecessary for user position and velocity computation. When time isoutside the range −7200 seconds<=t−TOE<=+7200 seconds, the satelliteposition accuracy is degraded and ephemeris data is not generally usefulfor autonomous position solutions.

Similar to almanac data, aged or inaccurate ephemeris data is useful forcomputing acquisition assistance information, such as Doppler and codephase estimates and satellite visibility estimates as a function oftime. The larger the time difference t-TOE the larger the error insatellite position and velocity coordinates. Equations describingephemeris developed position and velocity data are shown below in Eqns.(3) & (4).SVPosXYZ _(—) eph[sv]=SVPOS _(—) eph(t,wk,sv)  (3)SVVelXYZ _(—) eph[sv]=SVVEL _(—) eph(t,wk,sv)  (4)The satellite position and velocity equations used are as described inICD-GPS-200 document, Table 20-IV.

In one embodiment, the satellite position derived from ephemeris data iscompared to that derived from almanac data, for the same satellite andat the same time “t”. For example, the 3-dimensional difference vectorrepresented below by Eqn. (5)ΔPXYZ[sv]=|SVPOS _(—) eph(t,wk,sv)−SVPOS _(—) alm(t,wk,sv)|  (5)represents the linear range difference between the almanac-derivedposition and ephemeris-derived position, where the magnitude operator|.| is a shortcut notation for the square root of the sum of the squaresof each of the three vector difference elements.

FIG. 8 illustrates the growth of the difference in satellite positionvectors described in Eqn. (5) as a function of the age of ephemeris andalmanac data. The x-axis in FIG. 8 represents the age of thealmanac/ephemeris in days, while the Y-axis represents the satelliteposition vector difference, i.e., Eqn. (5), for all satellites in theGPS constellation at a particular epoch time. At day number zero, afresh almanac and ephemeris for the entire GPS constellation wascollected. When the almanac and ephemeris are fresh (day number 0, 1,2), the difference in satellite positions is relatively small, on theorder of 1-2 km. As the data sets age, the difference in satelliteposition derived from ephemeris as compared to almanac grows to be nomore than 300 km after about 100 days. Most of the difference is due toerror growth in satellite positions from the ephemeris data, not fromthe almanac data, because of the inclusion of the amplitude of sin andcosine corrections to arguments of latitude, orbital radius andinclination angle. Compared to the user-to-satellite range, which isbetween 20,100 km and 28,500 km, a 300 km position error in thesatellite position vector is very small compared to the geometry of theuser to satellite range ( 1/67^(th) to 1/95^(th) of the range vector).Thus, satellite visibility equations that describe the azimuth andelevation of a particular satellite as a function of time will be inerror by no more than approximately 1-2 degrees.

FIG. 9 shows the satellite velocity vector difference between ephemerisand almanac data as both age from their “fresh” state (day=0, 1, 2) tothe relatively old 100 days. Most of the satellite velocity vectordifference is in the along-track direction, but it could be in thedirection of the user-to-satellite unit vector which means it translatesdirectly to predicted Doppler error. After about 100 days, theworst-case velocity vector difference is less than 35 meters per second,which translates to about 183 Hz predicted Doppler error if all thevelocity error is in the direction of the user-to-satellite unit vector;a low probability case. Most of the difference shown in FIG. 9 is due tothe aging ephemeris data, not the aging almanac data. The predictedDoppler with 100 day-old ephemeris data is sufficient to acquiresatellites if the acquisition algorithm takes into account the nearlylinear growth in Doppler uncertainty due to the aging ephemeris data.For example, the acquisition algorithm could modify the Doppleruncertainty as a function of approximately ephemeris age, for example,Du=183 Hz*Days/100, and expand the Doppler search space accordinglybased on the age of the stored ephemeris data as it ages.

FIGS. 10 and 11 illustrate the satellite position and velocitydifference relationship of a current ephemeris data (day=0) compared toalmanac data that was current 80 days earlier. At t=−80 days, freshalmanac data is captured and stored in memory. At t=0 days, freshephemeris data is collected and compared to the older almanac data.After the ephemeris data is collected, one can plot theposition/velocity difference backwards in time, i.e., from T=−80 days(almanac fresh, ephemeris −80 days old) to T=0 days (ephemeris fresh,almanac 80 days old). This allows a direct comparison of the performanceof almanac data after 80 days of aging when the almanac positions andvelocities are compared to ephemeris positions and velocities when timeT is within the accurate ephemeris time period of −7200seconds<=t−TOE<=+7200 seconds. At day zero (x-axis), ephemeris data ismost accurate and the aging almanac is the source of most of theposition/velocity difference. FIG. 10 indicates that even after 80 daysof aging, almanac data still returns position data within 40 km, andvelocity accuracy within about 5 meters per second (FIG. 11) of truth,truth data being determined from the fresh ephemeris data.

In FIGS. 10 and 11, plots 1000, 1002, 1004 & 1006 represent error versustime for a group of four satellites, whose position and velocity errorsare substantially greater than the other 24 satellites in theconstellation. Periodically, satellites in the GPS constellation arere-phased or moved in the orbit to re-align the orbit for more optimumcoverage. As a result, in FIGS. 10 and 11, satellites corresponding toplots 1000, 1002, 1004 & 1006 have been re-phased in orbit some time inthe 80 days between acquisition of the almanac and ephemeris data. Thusthe old orbit was captured by the “old” almanac data, while the “new”orbit was captured by the “new” ephemeris data. Consequently, there is asubstantially large position and velocity error in re-phased satelliteposition and velocity comparisons between almanac and ephemeris data.This error is detectable by much larger than normal error growth overtime, and the fact that a particular satellite has been re-phased inorbit can also be detected by a much larger error than expected in theold almanac satellite position/velocity data compared to the newerephemeris satellite position/velocity data. The almanac data that isstored should probably be replaced with fresh almanac, or simply use thenewly gathered ephemeris data to acquire satellites. Attempts to use theold “pre-phasing” almanac or ephemeris data to acquire a satellite“post-rephasing” will likely result in failure to detect the satellitedue to a large estimated Doppler error.

According to another aspect of the disclosure, an SPS receiver downloadsephemeris, during normal usage, via a cellular network over-the-airprotocol message or directly from GPS satellites in order to computeaccurate position solutions at the SPS receiver. When new ephemeris isobtained, the SPS receiver compares the accuracy of the previouslystored almanac data to the fresh ephemeris data, and depending on anerror threshold, decides whether to replace the satellite's almanac datawith the ephemeris data or collect fresh almanac directly fromsatellites.

In some embodiments, the SPS receiver, which may be embedded in acommunications device, stores both almanac and ephemeris data for eachsatellite and compares the accuracy of the stored almanac data with thestored fresher ephemeris data, and decides to use either the almanacdata or the ephemeris data for each satellite acquisition assistcomputation dependent on the inaccuracy or error and/or age of almanacand ephemeris data. In another embodiment, the SPS receiver storesalmanac and ephemeris data for each satellite in the constellation, andcomputes assist data from the most accurate or fresh source, eitheralmanac or ephemeris data. A failure to detect a particular satelliteusing the assist data will trigger a request for fresh ephemeris for thenon-acquired satellite from a wireless network. In another embodiment,the SPS receiver stores ephemeris data for generation of satelliteacquisition assist at times outside the −7200 second<=t−TOE<=+7200 timeperiod. When the expected error in the assist data is greater than athreshold, the wireless handset requests fresh ephemeris for theparticular satellite. In still another embodiment, the SPS receiverstores ephemeris data for generation of satellite acquisition assist attimes outside the −7200 second<=t−TOE<=+7200 time period. When the ageof ephemeris exceeds a particular threshold after which the assist databecomes inaccurate, the GPS receiver embedded in the communicationsdevice requests fresh ephemeris for the particular satellite.

According to another aspect of the disclosure, a satellite positioningsystem receiver not attempting to acquire satellites, upon determiningthat ephemeris data for at least one satellite stored on the satellitepositioning system receiver is no longer useful for generating satelliteacquisition assistance data, the SPS receiver periodically updatesephemeris data, for example, from a communications network or directlyfrom the satellites, while the satellite positioning system receiver isnot attempting to acquire satellites until the satellite positioningsystem receiver has received updated ephemeris data for the at least onesatellite. In one embodiment, ephemeris data is updated while thesatellite positioning system receiver is not attempting to acquiresatellites until the satellite positioning system receiver has receivedupdated ephemeris data for all satellites.

According to another aspect of the disclosure, upon determining thatephemeris data stored on the satellite positioning system receiver isoutdated, a satellite positioning system receiver determines that aparticular satellite is visible using the outdated ephemeris data whilenot attempting to acquire satellites with the satellite positioningsystem receiver, and requests current ephemeris data for the samesatellite with a over-the-air message while not attempting to acquiresatellites with the satellite positioning system receiver. According toanother aspect of the disclosure, a satellite positioning systemreceiver determines that ephemeris data is too inaccurate to acquire asatellite by attempting to acquire the satellite using the storedephemeris data. If the ephemeris data is inaccurate, accurate ephemerisis requested in an over-the-air message.

According to another aspect of the disclosure, low-resolution satelliteorbital information is generated from information obtained from at leastone issue of ephemeris data. In some embodiments, the low-resolutionsatellite orbital information derived from information obtained from theat least one ephemeris issue has a resolution level sufficient forcomputing satellite location and velocity information. Satelliteposition and velocity information may be used to determine satelliteDoppler estimates and uncertainty ranges, which may be useful forinitial satellite acquisition by SPS receivers. In other embodiments,the low-resolution satellite orbital information derived from the atleast one issue of ephemeris data is substantially the same as almanacdata. Thus the low-resolution satellite orbital information is usefulfor SPS receivers not having previously stored almanac data, and inreceivers where previously stored almanac data becomes lost, corrupted,or outdated. This process may also eliminate the need to obtain almanacdata directly from the satellites or from an over-the-air message. Insome SPS receivers it is impractical for receiver manufacturers to storealmanac data or to store timely almanac data on the receiver. In theseand other instances it is desirable to generate low-resolution satelliteorbital information on SPS receivers.

Generally, a good approximation can be made to the almanac parametersfrom an ephemeris data set, at least for satellite acquisition purposes,by using the ephemeris data without regard to the amplitude of sin andcosine corrections to arguments of latitude, orbital radius, andinclination angle and limiting the orbit computation to the followingoriginal ephemeris parameters:

-   -   M₀—Mean Anomaly at Reference Time;    -   e—Eccentricity;    -   (A)^(1/2)—Square Root of the Semi-Major Axis;    -   (OMEGA)₀—Longitude of Ascending Node;    -   i₀—Inclination Angle at Reference Time;    -   ω—Argument of Perigee;    -   OMEGADOT—Rate of Right Ascension; and    -   IDOT—Rate of Inclination Angle.        It is generally acceptable to use ephemeris data for satellite        acquisition purposes during periods of time substantially        outside the +/−2-hour interval, for example, 100 or more days.

FIG. 6 illustrates a process for generating relatively low-resolutionsatellite orbital information from at least one issue of ephemeris datafrom the same satellite. The SPS receiver obtains multiple issues ofephemeris data EPH1 601, EPH2 602, EPH3 603 and EPH4 604, etc., from thesame satellite from time to time, for example, in connection with SPSreceiver position solutions. The ephemeris data may be acquired directlyfrom SPS satellites or it may be requested from some other source, forexample, from an assisted base-station via an over-the-air message. Theinterval between sequential issues of ephemeris data may be weeks ormonths, depending upon the resolution required of the low-resolutionsatellite orbital information derived therefrom, although longer orshorter time intervals may be used alternatively. The intervals betweenephemeris data issues preferably exceed the valid time period of anyparticular ephemeris issue, e.g., TOE+/−2 hours.

The multiple issues of ephemeris data are obtained during the normalcourse of SPS receiver operation, for example, when required fordetermining a position or location fix of the receiver. Thus, generally,it is unnecessary to allocate SPS receiver resources specifically toobtaining ephemeris data for the sole purpose of generatinglow-resolution satellite orbital information, since the ephemerisinformation is generally acquired for other purposes. In some instances,however, it may be desirable to obtain ephemeris data specifically foruse in generating or updating the resolution of the low-resolutionsatellite orbital information, for example, to ensure that the derivedlow-resolution satellite orbital information has the desired resolution.

In FIG. 6, ephemeris based satellite position and velocity is calculatedat block 610. The satellite position vectors (SVPosXYZ_eph[sv]) andsatellite velocity vectors (SVVelXYZ_eph[sv]) are artifacts of SPSposition determinations at particular time epoch based on thecorresponding ephemeris data. Preferably, for each ephemeris data set,at least one satellite position and velocity vector coordinate pair isstored in a database on the SPS receiver, as indicated at block 612.More particularly, the parameters stored include the satellite positionvector SVPosXYZ_eph[i], satellite velocity vector SVVelXYZ_eph[i],satellite identification (SVID[i]), the time associated with thesatellite position/velocity data (TOW[i]), the GPS week number (Wn[i]),and optionally the time of ephemeris (TOE[i]). The index [i] indicatesthe entry number in the database for the particular parameter, example;svid[i] the corresponding satellite ID for that entry. The TOE[i] may bestored instead of TOW provided that satellite position and velocity arecomputed at TOE time instead of TOW time. It is not likely that thenormal position computation function would actually compute time atexactly TOE time, so it is more practical to store TOW time associatedwith the time of computation of the satellite position/velocity data. Inapplications in which no additional calls of the ephemeris basedsatellite position and velocity function are used, the storage of TOEcan be avoided. The storage of TOW[i] may be avoided if additional callsof the ephemeris based satellite position and velocity function can betolerated, then it is easier to compute the position and velocitycoordinates at TOE time, which allows for simplification of the databasebecause TOW time would be stored as TOE time, which requires fewer bitssince it is an integer representation. If the SPS receiver is useddaily, the logic has the luxury to store data at some periodic rate, forexample, weekly. If the usage pattern is much more sparse, say once peryear, then every ephemeris data set acquired would be used to update thestored almanac parameters.

In FIG. 6, at block 614, the satellite orbital information is obtainedby a direct curve-fit function that forms a satellite position curve andsatellite velocity curve from the plurality of satellite positionvectors and velocity vectors as a function of time. Computation of theKeplerian orbit elements may be determined in the traditional way. Anexample of computing Keplerian orbital elements from satellite positionand velocity data points is discussed starting on page 61 in“Fundamentals of Astrodynamics”, by Bate, Mueller, and White, publishedby Dover Publications, 1971. The satellite orbital information is storedat block 618 and is used later for acquisition assist generation.

In some embodiments, portions of the corresponding plurality of issuesof ephemeris data received for the at least one satellite, for example,eliminating sine and cosine harmonic terms in order to remove thislong-term error source in the ephemeris orbit equations. This can beaccomplished by setting the amplitude of sin and cosine corrections toarguments of latitude, orbital radius, and inclination angle to zero

In some embodiments, the satellite orbital coefficients determined atblock 614 are converted to almanac data resolution and format forconvenience. It is not necessary to scale the determined satelliteorbital coefficients into the same number of bits and scale factortransmitted by GPS satellites. Scaling allows almanac data obtaineddirectly from GPS satellites or the satellite orbital coefficients to bestored in the same holding register by converting the satellite orbitalcoefficients into the format and resolution of almanac data. Also, theprecision of the plurality of issues of ephemeris data may be reduced toa resolution level comparable with almanac data for the same satelliteas described in U.S. Pat. No. 6,437,735.

According to another aspect of the disclosure, almanac data stored onthe SPS receiver is updated occasionally based upon differences inephemeris-based satellite position and velocity information andalmanac-based satellite position and velocity information. This strategyeliminates the necessity of downloading updated versions of almanacdata.

The almanac data may be initially stored in memory on the SPS receiverduring manufacture, for example, via a serial port connection prior toshipping from the factory. Alternately, almanac data could be installedin the SPS receiver when it is initially delivered to the user, forexample, upon activation of a SPS enabled cellular telephone. Thealmanac data may also be obtained directly from SPS satellites, forexample, using the synchronization scheme discussed above, or byconventional means requiring at least 12.5 minutes of continuoussatellite tracking, which can substantially drain the handset battery ifnot coupled to an external power source. According to this aspect of thedisclosure, however, it is only be necessary to obtain the almanac dataonce, regardless of the acquisition means.

This scheme takes advantage of the fact that the SPS receiveroccasionally acquires fresh ephemeris data for receiver positioncomputations. The ephemeris data may be acquired directly from SPSsatellites in about 30 seconds of continuous tracking, or it can berequested via an over-the-air message set from an assisted SPS basestation or from some other source.

In FIG. 7, the SPS receiver obtains multiple issues of ephemeris dataEPH1 701, EPH2 702, EPH3 703 and EPH4 704, etc., from the same satellitefrom time to time, for example, in connection with SPS receiver positionsolutions, separated by some time interval as discussed above inconnection with FIG. 6. As discussed, an artifact of positioncomputations is satellite position vector (SVPosXYZ_eph[i]) andsatellite velocity vector (SVVelXYZ_eph[i]) information for eachsatellite at a particular time epoch based on the fresh ephemeris data.In FIG. 7, satellite position vector SVPosXYZ_eph[i], satellite velocityvector SVVelXYZ_eph[i], satellite identification (SVID), time associatedwith the satellite position/velocity data (TOW[i]), GPS week number(Wn[i]), and optionally the time of ephemeris (TOE[i]) are stored atblock 712, as discussed above in relative to FIG. 6.

The ephemeris data creates relatively true satellite position andvelocity vectors during a portion of time bracketing the time ofephemeris (TOE) by two hours, i.e., TOE+/−2 hours. Thus any satelliteposition/velocity data derived from fresh ephemeris data at a time epochbetween or within the range of TOE+/−2 hours can be used as a “truthmodel” when compared to almanac-derived satellite position and velocityvector data for the same time epoch. As the stored almanac data ages,the error between the ephemeris and almanac derived position andvelocity vectors grows to some unacceptable limit. The differences, alsoreferred to as position and velocity residuals, can be used to computeadjustments to the originally stored almanac parameters to reduce thealmanac produced errors.

The process generally compares almanac derived satellite position andvelocity information to satellite position and velocity informationderived from current ephemeris data, and derives corrections for currentalmanac parameters based upon the comparison. The corrections are usedto update the almanac parameters (new_param=old_param+correction), forwhich the new parameters are stored for future acquisitions, forexample, acquisitions outside the window of applicability of the currentephemeris data.

Upon development of a database of several current and past satelliteposition coordinates for several satellites, almanac data error may bemeasured. In FIG. 7, the almanac data stored at block 720 and theSVID[i], TOW[i], and Wn[i] parameters stored at block 712 are used tocompute almanac-based satellite position SVPosXYZ_alm[i] and velocitySVvelXYZ_alm[i] coordinates using an almanac-based satellite positionand velocity calculator 722. The almanac position and velocityinformation is computed at the time indicated by TOW[i] for eachsatellite (SVID[i]), which is obtained from block 712. The almanac-basedcomputation results are stored at block 724.

In FIG. 7, at block 730, differences in satellite position and insatellite velocity vectors are computed. Specifically,ΔPXYZ[i]=SVPOS_eph(t, wk, sv)−SVPOS_alm(t, wk, sv) represents the 3dimensional difference vector in position based on current satelliteephemeris and the aging almanac position, and ΔVXYZ[i]=SVVel_eph(t, wk,sv)−SVVel_alm(t, wk, sv) represents the 3-dimensional difference invelocity based on current satellite ephemeris and the aging almanacvelocity. The residuals are computed and stored in a database for eachsatellite stored in database at steps 712 and 724.

The position and velocity residual information may be used as an errorsignal, which may be used to correct the aging almanac data. In FIG. 7,at block 734, parameters of the original almanac are adjusted by afunction based on the size of the residuals over the time intervalcorresponding to the samples in the truth model database. After eachadjustment of the almanac orbit parameters, the process can repeat,creating a new set of residuals for each satellite.

In one embodiment, the process uses Least-Squares (LS) computations, orit may be performed iteratively to minimize the number of iterations. Ifa LS computation approach is used, the problem is best solved throughcomputations and partial derivatives of the satellite and position errorvectors with respect to the orbital parameters, i.e., modeling firstorder, underlying sensitivities involved. It can also be performed bytesting sensitivities of each almanac parameter and by adjusting eachone dependent on the direction of the dominant error in the residuals.

For example, if most of the error is in the along-track direction, thenthe mean-motion parameter should be adjusted to minimize the along trackerror on subsequent iterations. The essentially linear error growth inalong-track position error can be attributed largely to amisrepresentation of a single orbital element, namely, the mean motionof the satellite. This parameter represents the linear angular rate ofgrowth of the projected path of the satellite in a circle whichcircumscribes the ellipse (along which its actual motion occurs) and isrelated to two parameters within the ephemeris, the semi-major axis, a,and the correction to mean motion, Δn, both appearing in the Equationsbelow:M=n(t−t _(p))  (6)n=μ/a ³ +Δn  (7)where “t” denotes time, “tp” denotes the time of perigee passage, “n” isthe mean motion, and “M” is the angle within the circumscribing circle,and where “μ” represents a gravitational constant.

Given a measurement of the along-track error component of the almanac bycomparison with a current ephemeris, a correction can be generated bymaking an adjustment to the mean motion parameter assumed by thealmanac, thereby reducing its dominant error component. Other parameterscan be also adjusted depending on the direction and size of the residualerror vectors.

As the process continues to refresh the stored almanac data, the olderephemeris based data stored in memory are replaced with newer positionand velocity information so that the process of measuring errors arebased mostly on newer ephemeris data collected in the future relative tothe date of the almanac data. The process thus measures the error growthof the stored almanac as it ages compared to the truth ephemeris. Someminimum number of stored data points per satellite needs to be collectedin memory.

In some instances, it may not be possible to update the almanac data,for example, in cases where the residuals are not sufficiently reducedby iteration. In these instances is may be necessary to acquire newalmanac data or to generate low-resolution satellite information fromephemeris data as discussed above.

Situations that may result in convergence of the residuals includeDepartment of Defense (DoD) satellite orbit changes (i.e., orbitre-phasing) within the time frame of the satellite position and velocityhistory data stored in database, for example, between the time of EPH2and EPH3. Since the time frame between the collection of EPH2 and EPH3position and velocity information may be relatively long, weeks ormonths, there is no sure way to know whether a satellite has beenre-orbited. In one embodiment, ephemeris data parameters that indicatewhether a satellite trajectory has been changed are stored. Examples ofparameters that may be stored to detect significant changes in satelliteorbits, such as may occur during the re-orbiting of a spacecraft,include any one or more of the following ephemeris parameters, amongothers, for detecting significant changes in satellite orbit:

-   -   M₀—Mean Anomaly at Reference Time;    -   e—Eccentricity;    -   (A)^(1/2)—Square Root of the Semi-Major Axis;    -   (OMEGA)₀—Longitude of Ascending Node;    -   i₀—Inclination Angle at Reference Time;    -   ω—Argument of Perigee;    -   OMEGADOT—Rate of Right Ascension; and    -   IDOT—Rate of Inclination Angle.        For each of these parameters, an expected guard band would be        created, basically a minimum and a maximum value that would        bracket the expected next value of the parameter given that no        re-orbit event occurred. When a next ephemeris data set is        acquired, for example, from the cellular network, each new        parameter would be tested against its expected guard-banded        range based on the previous history of ephemeris data. If any of        the above parameters exceeded its expected maximum or minimum        value, then it's likely that a re-orbit operation occurred since        the last ephemeris set was observed for this particular        satellite. Under these circumstances, it would be necessary to        replace any stored satellite position and velocity data derived        from the ephemeris data from the re-orbited satellite.

A particular handset must be used periodically for position fixing inorder for the handset to obtain current copies of all ephemeris data foracquired or visible satellites in order to compute an accurate positionsolution internally. Thus, depending on the usage pattern of aparticular handset, it may be used frequently enough to update thestored almanac or low-resolution satellite orbit parameters, or it maybe used so infrequently that the almanac or low-resolution satelliteorbit parameters get stale. Some method of updating the almanac data orlow-resolution satellite orbit parameters in low usage pattern handsetsis required.

The satellites in the GPS constellation are in an approximately 12-hourperiodic orbit that precesses about 4 minutes per day. This means thatthe same satellite appears at the same point of the sky 23 hours and 56minutes later (not 24 hours). Each satellite in the constellation risesand sets during different parts of the day. A handset that is used onetime per week, say at 8 AM local time, will obtain fresh ephemeris forthe satellites visible at that time, but not obtain ephemeris for othersatellites in the constellation. This is because the over-the-airprotocol messages in cellular AGPS assist transport fresh ephemeris datato the handset only for the satellites that are currently visible at theuser's approximate location. Since the constellation of visiblesatellites is not much different at 8 AM between adjacent weeks, thehandset will only obtain fresh ephemeris for the same satellites overand over again until the constellation slowly rotates relative to theuser's local clock. Consequently, it can take many months for othersatellites in the constellation to become visible to the handset becausethey are not visible to the handset at 8 AM local time, and will not bevisible at that time for many months. Consequently, it is possible forthe method disclosed herein to update a certain number of satellitesfrequently, and not update other satellites for a long time because thesatellites not updated are on a different visibility schedule relativeto the user's usage pattern.

One method to counter this aging rate difference is to program thehandset to recognize when certain satellites stored almanac or lowresolution satellite orbit parameters are getting old or stale, eitherbecause the handset is not being used for periodic positioncomputations, or because the usage pattern for position computation issuch that certain satellites are never updated. The handset can beprogrammed to determine when the satellites needing update are visible,by normal computation of satellite visibility using the aging almanac orlow-resolution satellite orbit parameters. In one embodiment, thehandset would not attempt to acquire the satellite, only recognize thatthe satellite with the aging almanac or low resolution satellite orbitparameters is presently visible using local time from a real-time clockor cellular over-the-air message, the handset's last known location or acellular over-the-air message intended for transporting approximateposition to the handset, and the aging almanac or low resolutionsatellite orbit parameters. Using this data, the handset can then knowwhen the satellite for which the almanac or low resolution satelliteorbit parameters are in need of update, and then request an ephemerisupdate for all satellites visible at that time. The handset would notnecessarily have to compute position, but still it can go through theover-the-air protocol exchange as if it was attempting a position fix.When the cellular network receives the request for fresh ephemeris data,all ephemeris data for satellites visible at that time, including thesatellite needing an update to its stored almanac or low-resolutionsatellite orbit parameters, would be transported to the handset. Thehandset could proceed to a position fix, or simply use the algorithmsdescribed in this disclosure to update the stored almanac orlow-resolution satellite orbit parameters to be used for satelliteacquisition assist if and when the handset or user needs to acquiresatellites and produce a position fix. This update procedure would beaccomplished without ever turning on the handset's internal GPSreceiver, the update process could be scheduled at times of the day whenlittle cellular over-the-air traffic was occurring (for example, 2 am),so that fresh almanac or low resolution satellite orbit parameters arealways available for every satellite in the constellation.

While the present disclosure and what are considered presently to be thebest modes of the inventions have been described in a manner thatestablishes possession thereof by the inventors and that enables thoseof ordinary skill in the art to make and use the inventions, it will beunderstood and appreciated that there are many equivalents to theexemplary embodiments disclosed herein and that myriad modifications andvariations may be made thereto without departing from the scope andspirit of the inventions, which are to be limited not by the exemplaryembodiments but by the appended claims.

1. A method in a satellite positioning system receiver having a battery,the method comprising: determining whether the receiver is connected toa power supply other than its battery; beginning reception of satellitepositioning system navigation data directly from a satellite only whenthe receiver is connected to a power supply other than its battery;storing the navigation data received in memory of the receiver.
 2. Themethod of claim 1, discontinuing reception of the satellite positioningsystem navigation data directly from a satellite if the receiver isdisconnected from the power supply other than its battery.
 3. The methodof claim 1, continuing reception of the satellite positioning systemnavigation data until reception of the navigation data is complete ifthe receiver is disconnected from the power supply other than itsbattery during reception of the navigation data.
 4. The method of claim3, continuing reception of the satellite positioning system navigationdata if the receiver is disconnected from its power supply other thanits battery only if a predetermined portion of the navigation data hasalready been received.
 5. The method of claim 1, receiving satellitepositioning system navigation data includes receiving almanacinformation directly from a satellite.
 6. The method of claim 1,receiving satellite positioning system navigation data includesreceiving ephemeris information directly from a satellite.
 7. Asatellite positioning system receiver having a battery, comprising: apower supply port capable of connecting the receiver to a power supplyother than the battery; the receiver programmed to determine whether thereceiver is connected to a power supply other than its battery; thereceiver programmed to begin reception of satellite positioning systemnavigation data directly from a satellite when the receiver is connectedto a power supply other than its battery, the receiver programmed todiscontinue reception of the satellite positioning system navigationdata directly from a satellite if the receiver is disconnected from thepower supply other than its battery.
 8. The receiver of claim 7, thereceiver programmed to continue reception of the satellite positioningsystem navigation data until reception of the navigation data iscomplete, before discontinuing reception of the satellite positioningsystem navigation data, if the receiver is disconnected from the powersupply other than its battery during reception of the navigation data.9. The receiver of claim 8, the receiver programmed to continuereception of the satellite positioning system navigation data, before ofdiscontinuing reception of the satellite positioning system navigationdata, if the receiver is disconnected from its power supply other thanits battery only if a predetermined portion of the navigation data hasalready been received.
 10. The receiver of claim 7, the receiverprogrammed to receive satellite positioning system navigation dataincluding almanac information directly from a satellite.
 11. Thereceiver of claim 7, receiving satellite positioning system navigationdata includes receiving ephemeris information directly from a satellite.